Hub for rotary wing aircraft and the like



Dec.'9; 1947. J. s. PECKER ETAL HUB FOR ROTARY WING AIRCRAFT AND THE LIKE Filed July 1'7, 194?: 8 Shee'ts-Sheet l JOSEPH anscxs/g, EDW/N A. PECKER,

Dec. 9,4947. J. 5; PECKER ETAL 2,432,441

HUB FOR ROTARY WING AIRCRAFT AND THE LIKE Filed July 17, 1943 8 Sheets-Sheet 2 @illlll Dec.-9, 1947. J, s, Ec EI'AL 2,432,441

HUB FOR ROTARY WING AIRCRAFT AND THE. LIKE Filed July 17, 1943 8 Sheets-Sheet 5 Dec. 9, 1947. v J. s. i=Ec'KE ETAL 2,432,441

HUB FOR ROTARY WING AIRCRAFT AND THE LIKE I Filed July 17, 1943 s Sheets-Sheet4 3 a vum'vbow Ci Momma/ Dec. 9, 1947. J. s. PECKER ETAL HUB FOR ROTARY WING AIRCRAFT AND THE LIKE Filed July 17, 1943 8 Sheets-Sheet 5 6 J K Wm mm m; m w d. m. k n $6 WW Q N mQ w %ma/ 3.

Dec. 9, 19473 5 J. s. PECKER'EI'AL 2,432,441

" HUB FOR ROTARY WING AIRCRAFT AND THE LIKE Filed July 17, 1943 8 Sheets-Sheet 6 Dec. 9, 1947. J. s. PECKER ETAL 2,432,441 HUB FOR ROTARY WING AIRCRAFT AND THE LIKE I Filed July 17, 1943 8 Shets-Sheet 7 JOSEPH awe/i; 4 EDWIN A. PEG/YER,

8 Sheets-Sheet 8 J. s. PECKEZR ETA HUB FQR ROTARY= WING AIRCRAFT AND THE LIKE Filed July 17, 1943 Dec. 9, 1947.

Patented Dec. 9, 1947 HUB FOR ROTARY WING AIRCRAFT AND THE LIKE I Joseph S. Pecker and Edwin A. Pecker, Philadelphia, Pa.

Application July 17, i943, Serial No. 495,196

19 Claims. 1 This invention concerns an aircraft of the rotary wing type, power driven or by autogyration. Such an aircraft is sustained in flight when power driven, i. e., both vertical and horizontal motion, or a combinat on of such motions being obtained by rotor blades which are supported and l driven by a vertical shaft actuated by the aircraft engine.

An object of the invention is to provide means by which a plurality of adjustments may be made both with regard to the plane of rotation of said 1 ,1

blades, and to the pitch of said blades.

' Another object of the invention includes the provision of means selectively operable to lock each pair of blades against relative rotation, or

to rotate each pair of blades in opposite direc- :Iii

'tions for increasing the pitch of one blade and for decreasing the pitch of the other blade of that pair during the rotation ofthe hub and wh le the aircraft is in flight or on the ground,

to thereby change the plane of rotation in which -i all of the blades are rotated.

A further obiect of the invention is to provide easily controllable means for changing while in flight, the plane of rotation of said blades by changing the pitch of the blades at least one pair of blades, i. e., the blades having the same long tudinal axis.

A still further obiect of the invention is to effect the above movements by easily controlled manual and/or power operated means located within the fuselage of the aircraft.

Further objects will appear hereinafter throu hout the specification.

In the drawings:

Figure 1 s a perspective view of a rotary wing aircraft of the general type to which this invention is particularly adapted;

Figure 2 is a perspective view of a hub for rotary aircraft constructed according to this invent on, with the blades. or wing spars abbreviated, and without the swash plate and control rods. for purposes of clarity;

Figure 3 is an end elevation of the hub;

, Figure 4 is a side elevation of the hub;

Fi ure 5 is a top plan view of the hub, certain on the line 9 9 of Figure 8;

Figure 15 is a vertical sectional view of the parts shown in Figure 14, but taken at right angles thereto;

Figure 16 is a vertical sectional view similar to Figure 7, but omitting all parts but the upper control unit, its supporting structure and its driving connections to the shafts;

Figure 17 is a vertical sectional view similar to Figure 8, but omitting all parts but the upper control unit, its driv ng connections to the shafts, and its tilting means, and

Figure 18 is a diagrammatical view showing the relative positionsof the blades when the aircraft is in flight.

In rotary wing aircraft such as the helicopter or Autogiro type, a plurality of blades are mounted for rotation about a common axis, located above the fuselage of the aircraft. The efliciency of these blades, i. e., their ability to maneuver the aircraft, and perform other functions, all contribute to the characteristics of the aircraft itself.

The hub herein described is intended to meet any one of a number of conditions which may be encountered during takin'goff, or when landing from a supporting surface, such as the ground, or which must be met dur ng flight. In order to provide a plurality of blades which will impart to the aircraft maximum maneuverability characteristics, even under the most difficult conditions, the accompanying drawings illustrate and the following description sets forth a structure which includes two or more blades which rotate in the same plane. For purposes of illustration. two pairs of blades are shown,,the two opposite blades of each pair being hinged upon a common center. It is to be understood, however, that with slight, modification and entirely within the scope of this invention, each pair of axis (or to change pitch), without affecting the pitch of the other pair of blades, which may remain in the position of pitch in which they have been previously adjusted. The pitch change of one or both pairs of blades may be made either in sequence or simultaneously, or a pitch change of one pair may be made, and all of said pitch changes may be efiected while the aircraft is on the ground, or while in flight, and

while the hub is being rotated, or even while stationary. Additionally, the individualpitchz'of each blade may be altered simultaneously from a zero angle, to any pitch desired, .such as to.

an autogyration angle.

The hub of this invention permits angular adjustment of each pair of blades whereby said blades may rotate about their common center,

but in opposite directions. When a pair of blades has been adjusted, the rotation of said pair of blades automatically sets the plane of rotation of said blades r I V In thedrawin'gs', the: fuselage l flis provided with doors H, o'nly one'of'which is shown,and with tricycle landing gear comprising-a ferward wheel unit 12 and side whe'eluhits 13; only one of the'latter being, hown} Any suitably constructed tail "spar. orboom may be provided, but we have shown an'openwork or truss type boom M which extends'rearwa'rdly from the"fuselage i and supports the anti-torque propeller 15. :This

propeller is driven bya shaft which may be connected with the main engine of theaircraft, or with any other suitable source -of;power, "not shown. g i i I The rotor drive shaft 16 is driven by the engine,

not shown, but which is preferably located within the fuselage I 0,,and this shaft is rigidly connected by bolts I and Iii-with thetwo-part rotor housingygener'ally indicated 'a I193 The rotor housing I9 is rotatably supported by the support bracket 20 which is provided with suitab 'side bearings having their inner raceway" 22 mounted 4 other two legs 48 and 49 supporting the other identically shaped block section It will therefore be noted that the two block sections 59, 5!, together with the legs, the twopart sleeve [9, and the semi-circular shelves, are composed of identical parts, which parts when assembled as shown in Figure may besecured together with suitable fastening means, such as the screws 52, 53, which extend through the bosses 54 and 55 formed on the block sections 50 and 55, and the shelf portions 44 and 45, respectively. It will be appreciated that all of the parts numbered l6, l9 and 44 to 53, respectively, are

- -'able clutch and change-gear mechanism may be in sleeve 23 which is ri'gidwiththe'shaft lii, and i an outer raceway 24 which i's h'oused"in the bracket 21!. Rockably connectedby 25 with the rotor housing 'l'9 "i's the inner rotary-ring 2B of the swash plate 21;""I he outer rotaryring '23 of the swash plate is connected by pins 29' with the inner'rotary rin 25'for'rocking movement about an axis substantia ly per endicular-to the axis defined by the pins 25.

The outer rotary ring 28 is provided with "a peripheral groove 3!] 'rotatably receiving a) complementary'key 31 in egral with the stationary (non-rotatable) ring 3201 the' 'swash plate.

Th swash plate may be tilted by the pilot from within the fuselage cab n by means" of control rods 33, shown 'to be' four in number." Tilting movement ofthe" swash plate is transmitted through two sets or pairs of control links stand 35. Each pair or links reconnected to one of the two control yokes of the hub, whereby the pitch of the pairs of rotor blades 36', 31 and 38', 39''may be controlled, and forcontrolling the angle of' interposed between the engine and the shaft l6, if desired.

Supported on the block sections when assembled, isa two-part hub casing having half portions 56, 51: These portions are fastened'by suitable fastening means i 58 which extend through flanges. 'Fastened-to the bottom ofthesehalf are each provided with flanges 6| which seat on stepped portions 52 of-the block sections-50 and 5!, asshown in-Figure '9.-

The block sections when assembled-as shown in Figure 9,-prcvide ,circu1ar'shoulders-63 which prevent sidewise movement 'of the circular housing 64 showndisassembled in Figure 10. This circular housing is provided with bearing sleeves 55 which snugly fit within bearing portions 66 of the-block sections. The circularhousingis further provided with extensions (ST-extending at right angles to said bearing sleeves. Said extensions forrn housings for bearing sleeves 68. Extending at right angles to the extensions 61, as shown in Figure 9, -are openings in the half portions 5% and 51, whichhouse bearing bushings 'l-il. There are also aligned openings, spherical in crcss section, numbered-84 and-85, which permit limited movement ofthe pitch control units hereinafter described. It will-therefore be noted from Figure 9 that each of the four shafts is provided with itsown bearing sleeve. Keyed to each shaft are inner bearing sleeves 7|. Each sleeve has fixed toits end a gear 12,13, 14 and 15.

As indicated in Figure 8, two standard variable pitch units are located, one above and one below the shafts 46, 4|, and 43, with their attached gears. The upper pitch control unit which may be an electricmotor or a fluid motor, is indicated by the numeral 76, and has attached to its shaft tively. When said upper pitch control unit 16 is energized through the gears 71, H and it rotates the shafts 42 and .43 in opposite. directions. a

Similarly, the lower pitch controlunit 18 when energized, rotates the shafts 40 and 4| in'opposite directions, due to the fact that its gear 79 meshes with gears '59 and 19" on the ends of the shafts M3 and M, respectively. This relative rotation or rocking movement in opposite directions occurs about an axis common to the shafts 42 and 43 when the upper pitch control unit 16 is energized, and a similar movement occurs with regard to shafts 40 and 4| when the lower pitch control unit this energized.- Hence, the pitch of each pair of blades attached'to said shafts 40 and 4|, or 42 and 43, will be equally increased. Upon rotation of the gear of either pitch control unit, the pair of blades which it drives will be simultaneously equally increased or decreased in pitch.

As will be noted from an inspection of Figures 7 and 10, each block section is provided with inclined side walls 68 for reasons hereinafter indicated.

A brake (not shown), may be applied to the drive shaft of each unit, whereby its gear H or 19 may be locked against rotation. We have not shown the brake because said brake is well known in this art and is what has been termed a variable pitch propeller unit, and includes a propeller gear reduction unit, a motor, and a brake such as shown in numerous patents in the art of variable pitch propeller blades.

When the circuit is completed to each motor, the brake is released and the brake of each motor is locked as soon as power is out off.

When the brake is applied to the drive shaft of the unit 16, the gear 11 is locked against rotation, and the unit 16 and the shafts 42 and 43, which are locked because the locked gear 11 is in mesh with the gears ll and 11'', may have tilting force applied, which tends to rock the blades 38 and 39.

in the same direction, this force being applied through the control yoke of the unit 76, as will hereinafter appear. When this tilting force becomes efiective in one direction, it causes the pitch of the blade 38 to be increased and the pitch of the blade 39 to be decreased. When this tilting force becomes effective in the opposite direction, it causes the pitch of the blade 38 to be decreased and the pitch of the blade 39 to be increased. During these applications of tilting force, circular unit 18 rocks clockwise or counterclockwise, as in Figure 8, about the common axis of shafts 42 and 43. When the brake is applied and when rocking movement occurs, the tilting force causes the pair of shafts, either 42 and 43 to rock or rotate in the same drection, and it will be understood that both actions may take place at the same time.

The means for applying this tilting force comprises the upper tilting yoke formed by the brackets 88 which are integral with the inner portion of the housing of the upper pitch control unit 18 (Figure 8), to which are secured upstanding studs 8| having the inner ends of arcuate arms 82 rigidly secured thereto.

The outer ends of the arms 82 are provided with clearance loops 83 with outwardly directed flanges forming the inner raceway of a ball bearing unit, having an outer raceway to wh ch the arms of the upper forked end of the control links 35 are pivotally connected (the similar lrwer control unit hereinafter described is shown in detail in Figure 13). Thus, when the outer stationary ring 32 of the swash plate, shown in Figures '7 and 8, is tilted in the appropriate direction by the pilot of the aircraft, through the control rods 33, tilting force is exerted through the control links 34, tending to tilt the common plane of the axis of blades 35,

31, 38 and 33 about the axis of shafts 48 and 4|.

Since the common plane of the axes of blades 38, 31, 38 and 39 represents the plane of rotation of the rotary blades, this tilting force tends to change the angle of incidence, or angle of attack thereof. It will be appreciated that when it is desired to cause the aircraft to move straight up or when coming down, the plane of said blades is substantially horizontal, as shown in Figure 1.

Secured to the inner end of the shaft 43 is the bearing sleeve 88 of the gear 11", as shown in Fig- 'ure 7. Likewise, the bearing sleeve 81 of the gear :11 is fixed to the shaft 42. These sleeves are journaled in bearing bushings 88 forming part'of extensions 81 of the circular housing 64 (Figure 10). Bearing bushings 88 form a support cradle for the lower pitch control unit 18, which is simition by means hereinafter described, the gears 19' and 19 and attached shafts 40 and 4| are rocked as a unit about the common axis of the shafts 43 and 4|, i. e., clockwise, or counter-clockwise, as seen in Figure 8. This swinging movement of the unit 18 about the axis of shafts 49 and 4| is limited by the clearance provided by the lower clearance opening in the circular housing 84, shown in Figure 7.

When the unit 18 is energized to rotate the gear 19 in either direction with the brake of said unit being off, the gears 19 and 19" and attached shafts 42 and 43 are rocked in opposite directions, reversely, either to increase the pitch of the rotor blades 38, 39 on both shafts 42 and 43, or to decrease the pitch thereof, simultaneously,

Thus, the pitch control unit 18 comprises means selectively operable to lock the shafts 42 and 43 against relative rotation and to thereby cause said shafts to be rotated in the same direction when said unit 19 is rocked clockwise or counterclockwise, as seen in Figure '7. Or reversely, and when the brake is released from the unit 18, and said unit is energized, to increase or decrease the pitch of the blades 38 and 39 on the shafts 42 and 43, concurrently. The pitch control unit 16 performs the same function with respect to the shafts 40 and 4| and the blades 36 and 31 fixed thereon.

The means for applying tilting force tending to tilt the lower pitch control unit 18 about the cornmon axis of the shafts 40 and 4|, i. e., clockwise 'or counter-clockwise, as seen in Figure '7, comof the casing 58, 51, thence upwardly to terminate in clearance loops 9| surrounding the shafts 42 and 43. These loops are each flanged to form the inner race of a ball bearing assembly (Figure 13) each having its outer race pivotally connected at 92 with the upper forked end 93 of the link 34. It will be understood that the control link 35 is formed with a forked end not shown, simiar to the link 34, shown in Figure 13, and the forked end is connected with the clearance loop of the arms 82, as shown in Figure 3.

Similarly, motor 16 has a support 88 to which arms 8| are attached at one of their ends, the opposite ends of these arms being attached to the upper tilting yoke formed by a pair of similar arms 82. Links 35 are connected by means of ball bearings to the hollow circular ends 83 of the arms 82.

The control links 34 and 35 are each formed of two parts which are connected by turn-buckles 94, and the lower ends of the links 34, 35 are spherical as indicated at 95. These spherical ends are adapted to engage in an aperture forming a spherical seat portion 96 located in the outer rotary ring 28, as indicated in Figures 7 and 8. The lower part of the aperture is provided with a screw plug 91 having a ball seat in its upper sur- 7 face. Thus, a ball and socket connects the control links 34 and 35 with the outer rotatable ring 28 of the swash plate 21.

The angle of rotor inclination is the angle between the plane of blade rotation defined by blades 36, 31, 33 and 39 with regard to the horizon or the terrestrial horizontal plane.

Operation In order to cause the aircraft to move forwardly or rearwardly, or any other translational movement, the swash plate is actuated as stated above. Assuming that the blades are rotating in a horizontal plane and that the pitch of each blade is zero, as shown in Figures 1 and 2, and it is desired to move forwardly, the swash plate is actuated so as to cause each pair of blades to have its pitch angle changed cyclically as the blades revolve on shaft 18. This continuous change of pitch angle is the feathering of the blades. The continued rotation of the blades after the pitch angle has been changed to three degrees, causes the blades to assume the position shown in Figure 18. In this position the leading edge of blade 38 is elevated and its trailing edge is depressed and the opposite blade 39 has its leadin edge depressed and its trailing edge elevated. Blades 35 and 3? which now extend at right angles to the direction of the straight arrow,'in this position are at zero pitch. Assuming that the blades are rotating clockwise as indicated by the curved arrow in Figure 18, when the blade 37 reaches the position where the blade 38 is shown, its inclination is the same as that shown for blade 33, and blade 3'? has now moved to the position of blade 35 with. its angle of inclination at zero pitch. Blade 36 has moved to the position indicated by blade 39 and its pitch is the same as that of blade 39 in Figure 18, and blade 39 has moved to the position of blade 31 and its angle of inclination is at zero pitch. The general result is to shift the center of lift of the rotor as a who e.

Substantially simultaneously with the adjustment of the pitch angle blades, and due to the universal support of the shafts 4i! and 4|, and 2 and 43, the adjustment has automatically caused the plane of rotation of the four blades to be changed. In other words, the manual changing of the pitch angle of the blades has caused the entire plane of rotation to be changed. The greater the adjustment pitch angle the greater will be the tendency of the angle of the plane of rotation to the horizontal. It will therefore be understood that each blade will feather twice during each revolution of said blade, or in other Words, during the time each blade has made a complete revolution with the drive shaft l6 as a center.

The balancing of the load and the pitch of the blades automatically sets the angle that the plane of rotation of said blades bears to the horizontal plane.

When viewing the aircraft from a point directly in front, and assuming that the swash plate has been adjusted for translational flight, and

with the blades rotating, it will be noted that a.

quarter mark the leading edge is at the same posi-- tion as at the one-quarterrevolution point. During this time, i. e., a 360 revolution about the shaft, each blade feathers twice, that is, rotates in one direction and back, then in the other direction and back, where its angle of attack becomes zero.

The above statement of operation has assumed that the pitch control units hate been locked so that their gears 11 and 19 cannot rotate. Also assuming that a pair of blades have been adjusted so that the pitch angle is three degrees from a horizontal plane of the blades which are supported on shafts All and 4|, upon release cf the brake of the unit 18 and upon energizat'on of said unit, the blades on said shaft may be adjusted so that one of said blades will have a zero angle of pitch and the other blade will have a six degree pitch angle, whereas in the same position before said adjustment, each blade had a three degree pitch angle.

By reference to Figures 2, 3 and 8, it will be noted that the casing 56, 5'! is provided with apertures 99 and tile for accommodation. of the arms 32 and 823, respectively.

While we have shown all the shafts 40, 4|, 42 and 43 as being mounted in the same plane, it is to be of course understood that it is within the scope of this invention to provide alternately only one pair of blades, or two pairs of blades, the shafts Ail and ti rotating in one plane, and locate the shafts 42 and 43 so as to rotate in a plane either above or below the plane of rotation of said shafts 4i! and El.

The word pitch as used in the cla ms relates to the angularity of the individual blades with respect to the plane of rotation of sa d rotary blades, and the angle of inclination of the rotary blades or plane of the same, as used in the claims, is the angle of the plane of rotation of said rotary blades with respect to the horizon or the terres trial horizontal plane.

It Will be understood thatthe above description and the accompanying drawings illustrate only one form of the invention, and that we do not desire to be limited in the practice of this invention except as defined by the appended claims.

Having thus described our invention, What we claim is:

1. In a rotor hub for rotary Wing aircraft, means for rotating said rotor hub, a, pair of aligned blades, each having a shaft mounted in said rotor hub rockable about a common axis, a second pair of aligned blades, each having a shaft mounted in said rotor hub rockable about a second axis coplanar with said first named axis, and manually controlled means for changing the mean pitch of one pair of blades without affecting the mean pitch of the other pair of blades.

2. In a rotor hub for rotary wing aircraft, means for rotating said rotor hub, a pair of aligned blades, each having a shaft mounted in said rotor hub rockable about a common axis, a second pair of al gned blades, each having a, shaft mounted in said rotor hub rockable about a second common axis perpendicular to said first named axis, and means for changing the mean pitch of one pair of blades without affecting the mean pitch of the other pair of blades.

3. In a rotor hub for rotary wing aircraft, means for rotating said rotor hub, a pair of aligned blades, each having a shaft mounted in said rotor hub rockable about a common axis, a second pair of aligned blades, each having a shaft mounted in said rotor hub rockable about a secnected to the blade shafts for causing mean pitch change, and cyclic pitch changing means connected to the said power means.

4. In a universal hub, means for rotating said hub, a pair of aligned blades, each having a shaft mounted in said rotor hub rockable about a common axis, a second pair of aligned blades, each having a shaft mounted in said rotor hub rockable about a common axis coplanar with said first named common axis, power means directly connected to the blade shafts for causing mean pitch change of the blades, and cyclic pitch changing means connected to said power means.

5. In a hub for rotary wing aircraft and the like, a plurality of pairs of coaxial rotor wing blade carrying spars, means selectively operable to rock one pair of blade spars for varying the pitch without afiecting the mean pitch adjustment of another pair of blade spars, or to lock said each pair of spars against rocking movement with respect to their common axis, and means for cyclically varying the pitch of each blade.

6. In a hub for rotary wing aircraft and the like, means for rotating said hub, a plurality of pairs of coaxial shafts supported by said hub, each shaft having a blade, manual means for cyclically changing the pitch of all of said blades, and selective means for independently rocking either pair of blades in the same direction to change the mean pitch whereby to increase or decrease the angle of attack of the blades on opposite shafts of that pair of shafts.

'7. In a hub for rotary wing aircraft and the like, means for rotating said hub, a plurality of pairs of coaxial shafts supported by said hub, each shaft having a blade, manual means for cyclically changing the pitch of all of said blades, and selective means for changing the mean pitch of each pair of blades without affecting the mean blade pitch of another pair of blades to change the mean pitch whereby to increase or decrease the angle of attack of the blades on opposite shafts of that pair of shafts, said selective means including a pitch changing unit, in direct driving relation with a pair of said coaxial shafts.

8. In a hub for rotary wing aircraft and the like, means for rotating said hub, a plurality of pairs of coaxial shafts supported by said hub, each shaft having a blade, manual means for cyclically changing the pitch of all of said blades, and selective means for changing the mean pitch of each pair of blades without affecting the mean blade pitch of another pair of blades to change the mean pitch whereby to increase or decrease the angle of attack of the blades on opposite shafts of that pair of shafts, said selective means including a separate pitch changing unit for each pair of shafts, in direct driving relation with a pair of said coaxial shafts.

9. In a hub for rotary wing aircraft and the like, means for rotating said hub, a plurality of pairs of coaxial shafts supported by said hub, each shaft having a blade, manual means for cyclically changing the pitch of all of said blades, and selective means for changing the mean pitch of each pair of blades without affecting the mean blade pitch of another pair of blades to change the mean pitch whereby to increase or decrease the angle of attack of the blades on opposite shafts of that pair of shafts, said selective means including a pitch changing unit, said unit including a motor having a shaft drivingly connected to one of said pairs of shafts.

10. In a hub for rotary wing aircraft and the like, means for rotating" said hub, a plurality of pairs of coaxial shafts supported by said hub,

each shaft having a blade, manual means for cyclically changing the pitch of all of said blades,

' and selective means for changing the mean pitch of each pair of blades without affecting the mean blade pitch of another pair of blades to change the mean pitch whereby to increase or decrease the angle of attack of the blades on opposite shafts of that pair of shafts, said selective means including a separate pitch changing unit for each pair of shafts, each unit including a motor having a shaft drivingly connected to a pair of shafts.

11. In a, hub for rotary wing aircraft, means for rotating said hub, a plurality of pairs of shafts mounted on said hub, blades on said shafts, independent means selectively operable to rock the blades of either pair of shafts or to lock the blades of either pair of shafts against rocking movement, and means for cyclically varying the pitch of each of said blades.

12. In a hub for rotary wing aircraft, means for rotating said hub, a plurality of pairs of shafts mounted on said hub, blades on said shafts, independent means selectively operable to rock the blades of either pair of shafts or to lock the blades of either pair of shafts against rocking movement and means for cyclically varying the pitch of each of said blades, said selectively operable means including a pitch changing unit.

13. In a hub for rotary wing aircraft, means for rotating said hub, a plurality of pairs of shafts mounted on said hub, blades on said shafts, independent means selectively operable to rock the blades of either pair of shafts or to lock the blades of either pair of shafts against rocking movement, and means for cyclically varying the pitch of each of said blades, said selectively operable means including a separate pitch changing unit for each pair of shafts.

14. In a hub for rotary wing aircraft, means for rotating said hub, a plurality of pairs of shafts mounted on said hub, blades on said shafts, independent means selectively operable to rock the blades of either pair of shafts or to lock the blades of etiher pair of shafts against rocking movement and means for cyclically varying the pitch of each of said blades, said selectively operable means including a pitch changing unit, said unit including a motor having a shaft drivingly connected to at least one pair of shafts.

15. In a hub for rotary wing aircraft, means for rotating said hub, a plurality of pairs of shafts mounted on said hub, blades on said shafts, means selectively operable to rock the blades of either pair of shafts or to lock the blades of either pair of shafts against rocking movement and means for cyclically varying the pitch of each of said blades, said selectively operable means including a separate pitch changing unit for each pair of shafts, each unit including a motor having a shaft drivingly connected to a pair of shafts.

16. In a hub for rotary wing aircraft, means for rotating said hub, a plurality of pairs of shafts mounted on said hub, blades on said shafts, means selectively operable to rock the blades of either pair of shafts or to lock the blades of either pair of shafts against rocking movement and means for cyclically varying the pitch of each of said blades, said selectively operable means including a separate pitch changing unit for each pair of shafts, each unit including a motor having a shaft drivingly connected to a pair of shafts, one of said units being mounted above and the other being mounted below said shafts.

1 1 17;:In a hubfor rotary wing-aircraft, means for rotating said hub, a plurality of shafts mounted on said hub, blades on said shafts, manual means for changing the mean pitch of at least one of said blades without'aifecting the mean pitch of an other of said blades, and means for cyclically changing the pitch of all of said blades.

18. In a rotary wing aircraft, a hub, means for rotating said hub, a pair of shafts mounted on said hub, blades on said shafts, means selectively operable to rock the blades of said pair of shafts or to lock'the blades and said shafts against rocking movement, and means for cyclically varying the pitch of said pair of blades, said selectively operable means including a pitch changing unit for said pair of blades positioned by said cyclically varying means, said unit including a motor having a shaft drivingly connected to said shafts.

19. In a rotary wing aircraft, a hub, means for rotating said hub, apair of shafts mounted onsaid hub, blades on said shafts, means selectively operable to rockthe blades of said pair of shafts or to lock the blades and said shafts against rocking movement, and means for cyclically varying the pitch of said pair of blades, said selectively operable means including a pitch changing unit 12 for saidpair of blades-positioned by said cyclically varying means, said unit'including a motor having a shaft drivingly connected to the ends of said shafts.

JOSEPH S. PECKER. EDWIN A. PECKER.

REFERENCES CITED The following references are of record in the file of this patent:

UNITED STATES PATENTS Sweden Mar. 2, 1939 

